Thrust Enabling Objective System

ABSTRACT

An automatic emergency radar and proximity sensor activated protection system that could assist to prevent commercial, private, or military aircraft jet engines from being damaged or destroyed. 
     This is accomplished by the installment of a Shielding Blade Assembly which will immediately close when detection of objects such as; birds, debris, or other destructive elements try to enter through the engine intake while the aircraft is in FLIGHT. 
     When the Shielding Blade Assembly is closed, an Internal Air Injection Unit (A.I.U.) will supply high volumes of air in order for the engine to stay operational and prevent it from stalling while in FLIGHT. 
     Pilot and crew can then take all the necessary precautionary steps required until the aircraft with passengers and/or cargo can safely reach and land at the nearest available airport.

BACKGROUND OF THE INVENTION

For as long as the jet engine has existed, it has always been plagued by the uncertainty that at any given moment while in flight, the engine or engines of an aircraft could be compromised by external forces. This could normally occur at takeoff when aircraft are most vulnerable to things such as bird strikes or loose debris picked up off the runway. Severe weather fronts containing heavy snow and ice, large hail, or wind shear can be destructive to any jet engine.

Currently, most of the more sophisticated jet engines have ice breakers located on the front intake of the main engine section. Deicing and heating systems are also part of similar designs. Unfortunately those preventive systems can only do a fraction of the job and may not be enough when something more overwhelming is about to compromise a jet engine during flight.

If a jet engine was to be equipped with a fully automated system that could detect incoming objects, be able to close and shield the intake of the engine, and alternatively supply air to the jet engine(s), then that is where the Thrust Enabling Objective System (T.E.O.S.) would come into play and could conceivably change the level of jet engine vulnerability making air travel safer for all.

BRIEF SUMMARY OF THE INVENTION

The importance of such an invention is to ensure the safety of a jet aircraft (commercial, private, or military) as well as those who are onboard while in flight by providing a system which automatically blocks out any object which would be destructive to the jet engine(s).

System could be activated automatically using an array of sophisticated sensors capable of detecting oncoming threats from long distances. Have the necessary safeguards to making certain that the only element going into the intake of the jet engine is air. To offer the same protective system to older existing jet engines still in operation while incorporate the same system when developing new jet engine designs.

BRIEF DESCRIPTION OF THE DRAWINGS TEOS-001ThrustEnablinqObjectivePresentation.pdf Drawing Sheet 01/01:

FIG. 1 is a Top View representing a twin engine commercial aircraft as it would look with the Thrust Enabling Objective System installed.

FIG. 2 is a Right Isometric View of the aircraft.

FIG. 2A is an enlarged detail view of the left or port side engine.

FIG. 3 is a Left Isometric View of the aircraft.

FIG. 3A is an enlarged detail view of the right or starboard side engine.

FIG. 4 is a Front View of the aircraft shown with the engines closed, Thrust Enabling Objective System on.

FIG. 5 is a Front View of the aircraft shown with the engines open, Thrust Enabling Objective System off.

TEOS-002ProximitySensorArravElectonics.pdf Drawing Sheet 01/03:

FIG. 1 Right Isometric View showing physical location of how Proximity Sensors 1, are mounted in front of the Extended Nacelle 10.

Drawing Sheet 02/03

FIG. 2 Plan view of block diagram for associated electronic systems used to monitor and operate the Proximity Sensor Array 1, Shielding Blade Assembly 20, and Internal Air Injection Unit 50 (one per engine), part of the Thrust Enabling Objective System.

Drawing Sheet 03/03:

FIG. 3 Right Side Elevation View showing proposed distance cone for Proximity Sensors mounted on front of Extended Nacelle.

FIG. 4 Front View showing proposed circumference of cone for Proximity Sensors mounted on front of Extended Nacelle.

TEOS-003ExtendedNacellewithAirIntakeAssembly.pdf Drawing Sheet 01/03:

FIG. 1 Exploded Right Isometric View of engine components (hidden line) with Extended Nacelle with Air Intake Assembly 10 (shown in solid), exterior air inlet doors open.

Drawing Sheet 02/03:

FIG. 2 Exploded Left Isometric View of engine components (hidden line) with Extended Nacelle with Air Intake Assembly 10 (shown in solid), exterior air inlet doors closed.

Drawing Sheet 03/03:

FIG. 3 Exploded Right Isometric View of Extended Nacelle with Air Intake Assembly components.

FIG. 4 Right Side Elevation with breakaway view showing location of Extended Nacelle with Air Intake Assembly internal components.

TEOS-004ShieldingBladeAssembly.pdf Drawing Sheet 01/05:

FIG. 1 Exploded Right Isometric View of engine components (hidden line) with Shielding Blade Assembly 20, (shown in solid), closed.

Drawing Sheet 02/05:

FIG. 2 Exploded Left Isometric View of engine components (hidden line) with Extended Nacelle Intake Assembly 20 (shown in solid), open.

Drawing Sheet 03/05:

FIG. 3 Exploded Right Side Elevation view of Shielding Blade Assembly components.

Drawing Sheet 04/05:

FIG. 4 Partial First Section, Exploded Right Isometric view of Shielding Blade Assembly components.

Drawing Sheet 05/05:

FIG. 5 Partial Second Section, Exploded Right Isometric view of Shielding Blade Assembly components.

TEOS-005InternalAirInjectionUnitAssembly.pdf Drawing Sheet 01/04:

FIG. 1 Exploded Right Isometric View of engine components (hidden line) with Internal Air Injection Unit Assembly 50, (shown in solid).

Drawing Sheet 02/04:

FIG. 2 Exploded Left Isometric View of engine components (hidden line) with Internal Air Injection Unit Assembly 50, (shown in solid).

Drawing Sheet 03/04:

FIG. 3 Exploded Right Isometric View of Air Injection Unit Assembly 50, main components.

Drawing Sheet 04/04:

FIG. 4 Exploded Right Isometric View of Impeller Cage Assembly 53, components.

DETAILED DESCRIPTION OF THE INVENTION

PROXIMITY SENSOR ARRAY with ELECTRONICS:

TEOS-002ProximitySensorArrayElectronics.pdf

FIG. 1 Sheet 01/03

The process of detecting any solid mass while in flight begins with the Proximity Sensor Array 1.

It is mechanically fastened to the annular air inlet port of the Extended Nacelle with Air Intake Assembly 10.

Inventors Note:

It is my intention to showcase a commercial aircraft equipped with two jet engines. Everything shown in FIG. 2 is laid out to reflect that application.

FIG. 2 Sheet 02/03

The Proximity Sensor Array 1, is electrically coupled to a Cockpit Display Panel 1 a. This panel will house a frequency transducer that will transmit continuous signal waves that when bounced off of an object will reflect echoes back to the Proximity Sensor Array where they are collected and translated back at the Cockpit Display Panel into a real-time map that will show both distance and time to possible impact.

Both an audible 1 b, and a visual 1 c, alert device will call attention to the cockpit crew.

As soon as an object is within strike distance, the onboard microcomputer and logic controller 1 d, will begin the task of preparing the jet engine(s) for an impact. As part of the failsafe design, each jet engine on an aircraft will have its' own SBA (Shielding Blade Assembly) Motor Drive Circuit 1 e, or 1 f, (see inventors note) so that each engine can be activated only if the threat to that engine is real.

At the moment the Shielding Blade Assembly 20, is activated, feedback from this unit will be transmitted back to the microcomputer and logic controller 1 d, and the AIU (Air Injection Unit) Motor Drive Circuit 1 h, or 1 j, (see inventors note) will power up and begin spinning the Air Injection Unit 50, which will bring outside air to supply the jet engine(s) and keep it from stalling during flight.

Anyone from the cockpit crew that attempts to override the system, will be locked out by a Test & Override Cockpit Function Controls 1 g. No shutdown will be permitted whether intentional or accidental. Once the system has been activated it will continue to function automatically until by which time the system detects no further threats and deactivates the override prevent functions when it is safe once again.

Extended Nacelle with Air Intake Assembly:

TEOS-003 Extended Nacelle with Air Intake Assembly.pdf

FIG. 3 Sheet 03/03

The Extended Nacelle Housing 11, will be one of the components which will be primarily designed and fabricated by the jet engine manufacturers to adapt the Thrust Enabling Objective System to their particular engine designs.

The Extended Nacelle Housing 11, will have (6) air entry ports located around its' exterior circumference.

Each one of the air entry ports will be covered by an Air Entry Door 12.

Behind each of the air entry doors, will be a Replaceable Multi-Stage Air Filter 13.

Each one of the air entry doors will be opened and closed by its' own Pneumatic Linear Actuator 14.

All supply and return lines (not shown) will be routed in such a way where it will not interfere with the operation of other components associated to the Thrust Enabling Objective System. This will also hold true if determined that a hydraulic (oil) system is to be implemented instead of a pneumatic (air) system.

Shielding Blade Assembly:

TEOS-004 Shielding Blade Assembly.pdf

FIG. 3 Sheet 03/05 FIG. 4 Sheet 04/05 FIG. 5 Sheet 05/05

Rear Mounting Ring 21, requires the installation of a Double Sealed Ball Bearing 22, at 5 locations around the ring before further assembly.

Press the Main Drive Gear Oil-less Bearing 25, onto the Center Support Hub 23.

Next slip the Main Drive Gear 26, over the Main Drive Gear Oil-less Bearing 25, and finish the Center Support Hub 23, assembly out by placing and temporarily retaining the Bearing Stop Ring 27, against the Main Drive Gear 26.

Center Support Hub 23, is positioned flange side up and the inside face of the Rear Mounting Ring 21, is placed against the flange side of the Center Support Hub 23, and secured with required Socket Head Cap Screws 24 (refer to sheet 05/05 for total number of 24). Make sure to line up all threaded holes and clearance holes between parts.

Lay the Rear Mounting Ring 21, with attached Center Support Hub 23, on its' rear face for the following steps.

The Front Mounting Ring 28, requires the installation of a Double Sealed Ball Bearing 29, at 5 locations around the ring before further assembly.

Insert 40 Tooth Driven Gear Pinion Assembly 31, into each of the (5) installed Double Sealed Ball Bearings 22, on the Rear Mounting Ring 21. Position the Front Mounting Ring 28, against face of Center Support Hub 23, (the side where the Bearing Stop Ring 27 is installed.)

Make sure to remove any temporary retainers that are holding the Bearing Stop Ring 27 for the next step.

Position the Bearing Stop Ring 27 onto the machined step of the Center Support Hub 23. Make certain that all 40 Tooth Driven Gear Pinion Assemblies 31, pass through the mounted Double Sealed Ball Bearings 29. The Front Mounting Ring 28, should lay flat against the Bearing Stop Ring 27.

Using Socket Head Cap Screws 30, (refer to sheet 04/05 for total number of 30) fasten Front Mounting Ring 28, to Center Support Hub 23, making sure to line up all threaded holes and clearance holes between parts as performed in the previous step with the Rear Mounting Ring 21.

It is important that the 40 Tooth Driven Gear Pinion Assemblies 31, turn freely when the Main Drive Gear 26, is spun manually on the Center Support Hub 23.

Without moving the partially assembled Shielding Blade Assembly 20, place one 4^(th) Stage Blade 32, onto each of the (5) shafts of the 40 Tooth Driven Gear Pinion Assemblies 31. Place a Teflon Pancake Washer 33, on top of each of the 4^(th) Stage Blades 32. Repeat this operation for the 3^(rd) Stage Blades 34, followed by another Teflon Pancake Washer 33.

Continue with the 2^(nd) Stage Blades 35, followed by another Teflon Pancake Washer 33, and end with the 1^(st) Stage Blades 36.

(Make certain that the blades lie concentrically between the inner and outer diameters of both Front Mounting Ring 28 and Rear Mounting Ring 21, and that all the raised drive coins on the blades are not riding up, and seat correctly to contact the drive slots).

With all the Blade Assemblies in the open (rest) position around the Front Mounting Ring 28, and Rear Mounting Ring 21, install a Drive Cog 37, onto each shaft of the 40 Tooth Driven Gear Pinion Assemblies 31. Each Drive Cog is keyed and has protruding drive cogs on the back side that must be located correctly and must secure each of the (5) sets of 4 blades onto the 40 Tooth Driven Gear Pinion Assemblies 31. Secure each Drive Cog by placing a Thrust Washer 38 on top and bolt each Drive Cog to the end of the 40 Tooth Driven Gear Pinion Assemblies 31, with Socket Head Cap Screws 39.

Using an overhead crane or suitable lifting mechanism, pick up the partially assembled Shielding Blade Assembly 20, and place it vertically to where it is accessible for mounting the next components.

Place a Drive Motor 40, into each of the mounting holes located on the top and bottom of the Rear Mounting Ring 21. Secure with required hardware (not shown) and then place a 52 Tooth Motor Drive Gear 19, on each of the Drive Motors 40. Secure Motor Drive Gear 19, with the appropriate hardware as required and specified by the motor manufacturer (not shown).

The completed Shielding Blade Assembly 20, will then be supported in a manner that is to simulate the same mounting apparatus that will be used to support the unit when mounted on a jet engine. The next step will be to fully test the assembled unit. Power will be fed to activate and make certain that the Drive Motors 40, operate smoothly, the Main Drive Gear 26, rotates against the Oil less Bearing 25, without binding, and that all 40 Tooth Driven Gear Pinion Assemblies 31, operate each of the (5) Stage Blade Assemblies 32, 34, 35, & 36, without binding or stalling.

Internal Air Injection Unit Assembly:

TEOS-005 Internal Air Injection Unit Assembly.pdf

FIG. 3 Sheet 03/04

Begin by assembling (2) Low Profile Pancake Motors 55, by installing a High Speed Friction Drive 54, onto the output shaft of each motor making certain the High Speed Friction Drives are pressed in and seat correctly on the shafts and are perpendicular to the shaft ends.

Next place each Low Profile Pancake Motor 55, inside the Rear AIU Main Casing Half 52, and place all (8) mounting bolts (not shown) from the rear side of the Rear AIU Main Casing Half 52, but do not tighten since it will require that the motors be pushed up against the drive ring on the Rear Impeller Rail 58, when the Air Injection Impeller Cage Assembly 53, is positioned into the Rear AIU Main Casing Half 52.

FIG. 4 Sheet 04/04

Assemble the Air Injection Impeller Cage Assembly 53, by placing the Rear Impeller Rail 58, face down (alignment grooves facing down) on a flat horizontal surface.

Press Rail Cage Bearing Shaft 60, into each of the (10) holes on the Rear Impeller Rail 58, then press 3.00″×1.25″×1.00″ Double Sealed Ball Bearings 61, onto each of the Rail Cage Bearing shafts 60.

Repeat the assembly procedure for the Front Impeller Rail 57, by first pressing Rail Cage Bearing Shaft 60, into each of the (10) holes on the Front Impeller Rail 57, and then pressing 3.00″×1.25″×1.00″ Double Sealed Ball Bearings 61, onto each of the Rail Cage Bearing Shafts 60.

Take the Rear Impeller Rail 58, and turn it (alignment grooves facing up) and lay on a flat horizontal surface. Place the Intake Impeller Blades 59 one at a time into each of the (36) alignment grooves around the circular sector of the Rear Impeller Rail 58.

Fasten with the appropriate hardware required (not shown), then when all (36) Intake Impeller Blades are secured to the Rear Impeller Rail 58, place the Front Impeller Rail 57, on top of the open end of the Intake Impeller Blades 59, and fasten in the same manner as previously done with the Rear Impeller Rail 58. (Alignment grooves facing down, bearings facing towards you).

FIG. 3 Sheet 03/04

Take the assembled Air Injection Impeller Cage Assembly 53, and place it concentrically within the Rear A.I.U. Main Casing Half 52. Make certain that all of the ball bearings installed on the Rear Impeller Rail 58, seat down into the roller groove on the Rear A.I.U. Main Casing Half 52.

Move both pancake motors previously installed inward until the High Speed Friction Drives 54, solidly contact the drive ring on the Rear Impeller Rail 58. Afterwards, tighten all (8) mounting bolts (not shown) sequentially until tight. Make sure that both of the High Speed Friction Drives 54, rotate freely when the Air Injection Impeller Cage Assembly 53, is spun manually.

Install “O” Ring Gasket (not shown) in groove of Rear A.I.U. Main Casing Half 52. Make certain that “O” Ring lays concentric within the groove and does not get rolled or pinched during the next step of assembly.

Place the Front A.I.U. Main Casing Half 51, on top of the partially assembled Rear A.I.U. Main Casing Half 52, and align all (12) of the retaining ears on both casing halves making sure that the “O” Ring does not get rolled or pinched and that the Double Sealed Ball Bearings 61, installed on the Front Cage Rail 57, seat into the roller groove of the Front A.I.U. Main Casing Half 51.

Secure the Front and Rear A.I.U. Main Casing Halves with 1.00″-14×15″ long Hex Bolts 56, at (6) places by passing the body of the bolt through the retaining ears on the Front A.I.U. Main Casing Half 51, and screw the bolts into the threaded holes on the Rear A.I.U. Main Casing Half 52. Make sure to properly sequence the tightening of all bolts so to eliminate the possibly of stress cracking any one of the retaining ears.

Make certain that when assembled, the Intake Impeller Cage Assembly 53, can spin freely as it is turned manually. The completed Internal Air Injection Unit 50, should be tested by properly supporting the unit as it would be installed and powered up so that the Low Profile Pancake Motors 55, High Speed Friction Drives 54, and Air Injection Impeller Cage Assembly 53, spins freely with no noises or vibration caused by imbalanced components. 

1. The Thrust Enabling Objective System-T.E.O.S. can be mounted on any type of jet engine. It can be retrofitted to protect older existing engines still in service and can be integrated into new jet engine design classes.
 2. The method according to claim 1, the physical size of the jet engine will not be a deterrent on whether an existing engine can be refitted with this system. The proximity sensor system along with the Shielding Blade Assembly and Internal Air Injection Unit can be tailored to each specific engine model.
 3. Each of the proximity sensor systems will be independent from the other engine(s), and only one individual engine could be activated if needed.
 4. The method according to claim 3, all controls and warning displays will be mounted in the flight cockpit allowing pilots to full control of the system including full override functions. If the system electronics warns that there is no time for pilots to take evasive action, the system overrides will become disabled and emergency activation will be automatic without interaction from the cockpit crew.
 5. The method according to claim 4, the electronic override of the system from pilot interaction will be effective as long as the aircraft is in FLIGHT and threat from an intake strike is eminent. Only when the aircraft has landed safely, will the manual override system controls once again become functional.
 6. The method according to claim 1, when retrofitting older jet engine models, the intake nacelle will be changed out and replaced with an extended section so the additional mechanicals for the Shielding Blade Assembly and Internal Air Injection Unit can be fitted within the required space.
 7. The method according to claim 6, the Internal Air Injection Unit (A.I.U.) will be matched to handle the thrust and load characteristics of each particular jet engine model. On existing jet engine models to be retrofitted, the Internal Air Injection Unit will again be part of the extended intake nacelle assembly mounted internally, inline immediately after the Shielding Blade Assembly and facing towards the compressor stages of the jet engine.
 8. The method according to claim 3, along with the array of proximity sensors, a Shielding Blade Assembly and Internal Air Injection Unit, will be installed as part of the new extended intake nacelle. The array of proximity sensors could also be complemented with other systems designed to detect objects nearing the intake of a jet engine. Infrared and thermal imaging, are such technologies that can help enhance the overall effectiveness of T.E.O.S. for extreme conditions. For even more enhanced detection, the use of high resolution Doppler radar could be incorporated into such a system.
 9. The Internal Air Injection Unit will have a multistage filtering and evacuation design located to the outside of the extended intake nacelle which will block and eject foreign matter trying to pass through the engine intake while T.E.O.S. is active in FLIGHT.
 10. (canceled)
 11. The method according to claim 8, the state-of-the-art electronic circuitry used for T.E.O.S. will be programmed for complete sensor self-diagnostics prior to pre-flight check status at startup of the aircraft. The proximity transducers will be checked then calibrated by transmitting test echoes that will then be received through the sensors indicating a “GO” status on the array.
 12. The method according to claim 11, the same electronic circuitry will perform a complete check of the Shielding Blade Assembly and Internal Air Injection Unit mechanicals. This will be accomplished at the moment the engines are started by the APU (Auxiliary Power Unit) by which the Shielding Blade Assembly will be closed, the Internal Air Injection Unit will be activated, then the Shielding Blade Assembly will reopen, and the Internal Air Injection Unit will shut down thus ensuring that the system is fully operational prior to aircraft departure.
 13. The method according to claim 1, the Shielding Blade Assembly will be made easily accessible by removal of the extended intake nacelle allowing maintenance crews access to perform routine service and inspection, both on T.E.O.S. and main engine components.
 14. The method according to claim 13, the Internal Air Injection Unit shall be designed also for ease of accessibility again by the removal of the extended intake nacelle allowing maintenance crews total access to the interior of the main engine stages.
 15. The method according to claim 3, in order to allow sufficient time for T.E.O.S. to respond to an incoming threat, the area of detection will comprise of a proposed minimal distance of 1,320 feet (¼ mile) out from centerline of the engine intake “times” a cross sectional area of coverage which would “equal” half the wing span of the aircraft. Example: A radar detection cone where the circumference of the cone would be 174 ft.×1,320 ft, long starting at the centerline of the engine intake nacelle and then extending outwards. See sheet 3 (FIG. 3 and FIG. 4) of drawing TEOS-002 Proximity Sensor Array Electronics.PDF (The 174 ft. was taken from the wing span specifications of an Airbus A-320-200; 111 feet/2=55.5 feet×pi=174 foot circumference.) This can be varied to increase area of coverage.
 16. The Shielding Blade Assembly will employ sealing gaskets around the perimeter of each blade on both sides. The gaskets will be of a tough and durable material capable of sealing out small fragments that might try to penetrate passed the closed blades. The gaskets must also withstand extreme temperature changes, be flexible enough without distorting to where they may be compressed against mating blades in order to create an almost perfect sealing environment.
 17. (canceled)
 18. The method according to claim 7, it is perceived by the idea that the internal Air Injection Unit must provide enough of a high volume of air to the compressor stage of the engine, to where a safety factor of no less than 50% available thrust would be maintained while T.E.O.S. is active during FLIGHT.
 19. Jet engine equipped aircraft can and have fallen victim to such conditions as sudden and extreme wind burst disrupting normal air flow which would and can result in stalls or flame-out rendering the engine totally inoperable. The use of T.E.O.S would greatly lessen those possibilities by providing an automatic Shielding Blade Assembly to prevent against such destructive forces from altering normal air flow should it become necessary.
 20. Jet aircraft that once were deemed unsafe and risky to fly into harsh environments could be fitted with T.E.O.S. and have total control over such flight conditions. Such examples would include; observation and research jets that could enter and traverse a developing hurricane with an improved percentage of confidence that a stall or flame-out would now be a lesser probability. Jets used to study high attitude wind shear forces could now safely venture into these areas without provocation.
 21. Just as wind can be a destructive force to the air intake of a jet engine so can the possibility of hostile projectiles entering and destroying a jet engine can have the same destructive affects. Military jet aircraft in foreign territories can always encounter hostile forces whose intent is to disable and take out enemy fighters and bombers. T.E.O.S. could now provide a first line of defense against such threats, whether on the ground or in the air.
 22. Though the system is primarily designed to work by electrical sourcing it could be possible to design the Shielding Blade Assembly for pneumatic or hydraulic operation. This of course would require a totally different method due to the fact that now an air supply or hydraulic oil systems would have to be used and space made where to house it, also needing many feet of supply and return hoses, distribution manifolds, check and proportioning values and hydraulic sensors would have to be made part of this design. Even with that it would still take electrical for all the necessary sensors, displays, and activation systems involved.
 23. A destructive force such as wind is not the only element of nature that can cause unstable flying conditions. Others, such as heavy snow and hail can create similar hazards. Here is where T.E.O.S. could be equipped with heating and de-icing equipment inside the Internal Air Injection Unit (A.I.U.) helping to breakup and minimize these elements allowing for a more normal jet engine operation.
 24. Due to its' unique design configuration, the Thrust Enabling Objective System could be used to extinguish an engine fire while in flight thus preventing further spread of flames to critical areas including that of the wing tanks. Once the fire was out, the cockpit crew could try to restart the engine(s) safely and if the fire started again, then the system would be reactivated, again aiding to put out the fire.
 25. When severe weather due to extreme frigid temperatures threatens to ground aircraft and prevent them from take-off, T.E.O.S. could be used in jet engines using the following procedure: By closing the Shielding Blade Assembly and activating the Internal Air Injection Unit (AIU) equipped with onboard electric elements, heated air could then be blown into the compressor stage of the engine keeping vital components from freezing and allowing for normal start-up by making certain that all lubricated parts, fuel, electrical, and primary engine systems are all within safe operating levels.
 26. Another destructive force of nature which could render the status of an aircraft engine(s) inoperable with lasting consequences is ash from volcanic eruption. As an aircraft flies through an air space with floating volcanic ash particles, vital components such as fuel delivery, and igniter systems can become clogged and saturated by large amounts of ash accumulating as air and ash enter through the engine inlet duct. By using T.E.O.S. many crucial moving as well as stationary parts of a jet engine can be better protected from the deterioration caused by the ashes corrosive elements.
 27. The method according to claim 19, jet engines can be vulnerable to sudden and violent patterns of air while in flight, similar circumstances can occur while on the ground. On a busy airport runway system, jet aircraft sometimes taxi very close to each other and be affected by stray burst of exhaust from the close passing aircraft. This could now create a possible compressor stall due to the disruption of the normal airstream entering a jet engine inlet duct. The results could be either a stall or surge that would greatly alter the performance of a jet engine and could lead to destructive consequences. By installing exhaust gas detectors at the inlet duct, these would then activate T.E.O.S. by sealing off the intake and supplying a controlled passage of air to the compressor stage to help minimize a stall and help maintain regular power levels. 